[Federal Register Volume 61, Number 102 (Friday, May 24, 1996)]
[Rules and Regulations]
[Pages 26091-26094]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-12731]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-NM-85-AD; Amendment 39-9630; AD 96-11-05]
RIN 2120-AA64


Airworthiness Directives; Airbus Industrie Model A300, A300-600, 
and A310 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Airbus Industrie Model A300, A300-600, and A310 
series airplanes, that requires inspections to detect cracks in the 
lower spar axis of the pylons between ribs 6 and 7, and repair, if 
necessary. This amendment is prompted by reports that fatigue cracking 
has been found on the lower spar of the pylon. The actions specified by 
this AD are intended to prevent such fatigue cracking, which could 
result in reduced structural integrity of the lower spar of the pylon.

DATES: Effective June 28, 1996.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 28, 1996.

ADDRESSES: The service information referenced in this AD may be 
obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France. This information may be examined at the Federal 
Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of 
the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-2797; fax (206) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain Airbus Industrie Model 
A300, A300-600, and A310 series airplanes was published in the Federal 
Register on March 6, 1996 (61 FR 8892). That action proposed to require 
inspections to detect cracks in the lower spar axis of the pylons 
between ribs 6 and 7, and repair, if necessary.
    Interested persons have been afforded an opportunity to participate 
in the

[[Page 26092]]

making of this amendment. Due consideration has been given to the 
comments received.

Support for the Proposal

    One commenter supports the proposed rule.

Request To Revise Compliance Threshold for Inspection

    One commenter requests that the inspection threshold specified in 
paragraph (h) of the proposal be revised from 14,500 landings to 17,000 
landings for consistency with the threshold provided in Airbus Service 
Bulletin A300-54-6014, Revision 1, dated March 28, 1994.
    The FAA concurs with the commenter's request. The FAA's intent is 
that the inspection threshold and repetitive inspection interval 
specified in paragraph (h) of this AD parallel the threshold and 
interval recommended in the Airbus service bulletin. The FAA has 
revised paragraph (h) of the final rule to specify an inspection 
threshold of 17,000 landings. The repetitive inspection interval of 
14,500 landings, which was recommended in the Airbus service bulletin, 
remains unchanged in this final rule.

Correction of Service Bulletin Number

    The FAA has revised the reference to a service bulletin number that 
appeared in paragraph (i) of the proposed AD as Airbus Industrie 
Service Bulletin A300-54-2017. The correct service bulletin number is 
A310-54-2017.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes previously 
described. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    The FAA estimates that 99 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 8 work hours per 
airplane to accomplish the required actions, and that the average labor 
rate is $60 per work hour. Based on these figures, the cost impact of 
the AD on U.S. operators is estimated to be $47,520, or $480 per 
airplane, per inspection cycle.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the requirements of this AD 
action, and that no operator would accomplish those actions in the 
future if this AD were not adopted.
    Should an operator of a Model A300 series airplane elect to 
accomplish the optional modification that is provided by this AD 
action, it will take approximately 100 work hours to accomplish, at an 
average labor rate of $60 per work hour. The cost of required parts 
will be approximately $1,500 per airplane. Based on these figures, the 
cost impact of the optional modification for Model A300 series 
airplanes is estimated to be $7,500 per airplane.
    Should an operator of a Model A300-600 or A310 series airplane 
elect to accomplish the optional modification that is provided by this 
AD action, it will take approximately 110 work hours to accomplish, at 
an average labor rate of $60 per work hour. The cost of required parts 
will be approximately $1,500 per airplane. Based on these figures, the 
cost impact of the optional modification for Model A300-600 and A310 
series airplanes is estimated to be $8,100 per airplane.

Regulatory Impact

    The regulations adopted herein will not have substantial direct 
effects on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government. Therefore, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a 
significant economic impact, positive or negative, on a substantial 
number of small entities under the criteria of the Regulatory 
Flexibility Act. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

96-11-05  Airbus Industrie: Amendment 39-9630. Docket 95-NM-85-AD.

    Applicability: Model A300, A300-600, and A310 series airplanes; 
as listed in Airbus Industrie Service Bulletins A300-54-0073, A300-
54-6014, and A310-54-2017, all Revision 1, all dated March 28, 1994; 
certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (k) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent reduced structural integrity of the lower spar, 
accomplish the following:
    (a) For Model A300 series airplanes equipped with General 
Electric CF6-50C engines, and having pylons that have not been 
modified in accordance with Airbus Industrie Service Bulletin A300-
54-0080, Revision 1, dated January 16, 1995: Prior to the 
accumulation of 10,900 total landings, or within 500 landings after 
the effective date of this AD, whichever occurs later, perform an 
internal eddy current inspection to detect cracks in the lower spar 
axis of the pylons between ribs 6 and 7, in accordance with Airbus 
Industrie Service Bulletin A300-54-0073, Revision 1, dated March 28, 
1994.
    (1) If no crack is found, repeat the inspection thereafter at 
intervals not to exceed 6,700 landings.
    (2) If any crack is found that is less than 35 mm, prior to 
further flight, stop-drill the crack in accordance with the 
procedures specified in Section 51-41-10 of the Structural Repair 
Manual (SRM). Thereafter, prior to the accumulation of 250 landings 
after crack discovery, repair in accordance with the service 
bulletin. Prior to the accumulation of 17,900 landings after 
accomplishing the repair, perform an eddy current inspection to 
detect cracks at the stiffener ends, ribs 6 and 7, at the edge of 
the holes made during the repair and on the fasteners located at the 
edge of the doubler, in accordance with the service bulletin.

[[Page 26093]]

    (i) If no crack is found, repeat the inspection required by 
paragraph (a)(2) of this AD thereafter at intervals not to exceed 
15,000 landings.
    (ii) If any crack is found, prior to further flight, repair in 
accordance with a method approved by the Manager, Standardization 
Branch, ANM-113, FAA, Transport Airplane Directorate.
    (3) If any crack is found that is greater than or equal to 35 
mm, prior to further flight, repair in accordance with a method 
approved by the Manager, Standardization Branch, ANM-113.
    (b) For Model A300 series airplanes equipped with General 
Electric CF6-50C engines, and having pylons that have been modified 
in accordance with Airbus Industrie Service Bulletin A300-54-0080, 
Revision 1, dated January 16, 1995: Prior to the accumulation of 
30,300 landings since installation of the modification, or within 
500 landings after the effective date of this AD, whichever occurs 
later, perform an eddy current inspection to detect cracks in the 
lower spar axis of the pylons between ribs 6 and 7, in accordance 
with Airbus Industrie Service Bulletin A300-54-0073, Revision 1, 
dated March 28, 1994.
    (1) If no crack is found, repeat the eddy current inspection 
thereafter at intervals not to exceed 21,300 landings.
    (2) If any crack is found, prior to further flight, repair in 
accordance with a method approved by the Manager, Standardization 
Branch, ANM-113.
    (c) For Model A300 series airplanes equipped with Pratt & 
Whitney JT9D-59A engines, and having pylons that have not been 
modified in accordance with Airbus Industrie Service Bulletin A300-
54-0080, Revision 1, dated January 16, 1995: Prior to the 
accumulation of 8,600 total landings, or within 500 landings after 
the effective date of this AD, whichever occurs later, perform an 
internal eddy current inspection to detect cracks in the lower spar 
axis of the pylons between ribs 6 and 7, in accordance with Airbus 
Industrie Service Bulletin A300-54-0073, Revision 1, dated March 28, 
1994.
    (1) If no crack is found, repeat the inspection thereafter at 
intervals not to exceed 5,700 landings.
    (2) If any crack is found that is less than 35 mm, prior to 
further flight, stop-drill the crack in accordance with the 
procedures specified in Section 51-41-10 of the SRM. Thereafter, 
prior to the accumulation of 250 landings after crack discovery, 
repair in accordance with the service bulletin. Prior to the 
accumulation of 14,200 landings after accomplishing the repair, 
perform an eddy current inspection to detect cracks at the stiffener 
ends, ribs 6 and 7, at the edge of the holes made during the repair 
and on the fasteners located at the edge of the doubler, in 
accordance with the service bulletin.
    (i) If no crack is found, repeat the inspection required by 
paragraph (c)(2) of this AD thereafter at intervals not to exceed 
12,800 landings.
    (ii) If any crack is found, prior to further flight, repair in 
accordance with a method approved by the Manager, Standardization 
Branch, ANM-113.
    (3) If any crack is found that is greater than or equal to 35 
mm, prior to further flight, repair in accordance with a method 
approved by the Manager, Standardization Branch, ANM-113. -
    (d) For Model A300 series airplanes equipped with Pratt & 
Whitney JT9D-59A engines, and having pylons that have been modified 
in accordance with Airbus Industrie Service Bulletin A300-54-0080, 
Revision 1, dated January 16, 1995: Prior to the accumulation of 
24,000 landings since installation of the modification, or within 
500 landings after the effective date of this AD, whichever occurs 
later, perform an eddy current inspection to detect cracks in the 
lower spar axis of the pylons between ribs 6 and 7, in accordance 
with Airbus Industrie Service Bulletin A300-54-0073, Revision 1, 
dated March 28, 1994.
    (1) If no crack is found, repeat the eddy current inspection 
thereafter at intervals not to exceed 18,200 landings.
    (2) If any crack is found, prior to further flight, repair in 
accordance with a method approved by the Manager, Standardization 
Branch, ANM-113.
    (e) For Model A300-600 series airplanes equipped with General 
Electric CF6-80C2 engines, and having pylons that have not been 
modified in accordance with Airbus Industrie Service Bulletin A300-
54-6020, dated February 22, 1994: Prior to the accumulation of 9,400 
total landings, or within 500 landings after the effective date of 
this AD, whichever occurs later, perform an internal eddy current 
inspection to detect cracks in the lower spar axis of the pylons 
between ribs 6 and 7, in accordance with Airbus Industrie Service 
Bulletin A300-54-6014, Revision 1, dated March 28, 1994.
    (1) If no crack is found, repeat the inspection thereafter at 
intervals not to exceed 6,100 landings.
    (2) If any crack is found that is less than or equal to 35 mm, 
prior to further flight, stop-drill the crack in accordance with the 
procedures specified in Section 51-41-10 of the SRM. Thereafter, 
prior to the accumulation of 250 landings after crack discovery, 
repair in accordance with the service bulletin. Prior to the 
accumulation of 15,600 landings after accomplishing the repair, 
perform an eddy current inspection to detect cracks at the stiffener 
ends, ribs 6 and 7, at the edge of the holes made during the repair 
and on the fasteners located at the edge of the doubler, in 
accordance with the service bulletin.
    (i) If no crack is found, repeat the inspection required by 
paragraph (e)(2) of this AD thereafter at intervals not to exceed 
13,600 landings.
    (ii) If any crack is found, prior to further flight, repair in 
accordance with a method approved by the Manager, Standardization 
Branch, ANM-113.
    (3) If any crack is found that is greater than or equal to 35 
mm, prior to further flight, repair in accordance with a method 
approved by the Manager, Standardization Branch, ANM-113.
    (f) For Model A300-600 series airplanes equipped with General 
Electric CF6-80C2 engines, and having pylons that have been modified 
in accordance with Airbus Industrie Service Bulletin A300-54-6020, 
dated February 22, 1994: Prior to the accumulation of 26,400 
landings since installation of the modification, or within 500 
landings after the effective date of this AD, whichever occurs 
later, perform an eddy current inspection to detect cracks in the 
lower spar axis of the pylons between ribs 6 and 7, in accordance 
with Airbus Industrie Service Bulletin A300-54-6014, Revision 1, 
dated March 28, 1994.
    (1) If no crack is found, repeat the eddy current inspection 
thereafter at intervals not to exceed 19,400 landings.
    (2) If any crack is found, prior to further flight, repair in 
accordance with a method approved by the Manager, Standardization 
Branch, ANM-113.
    (g) For Model A300-600 series airplanes equipped with Pratt & 
Whitney JT9D-7R4 or PW 4000 engines, and having pylons that have not 
been modified in accordance with Airbus Industrie Service Bulletin 
A300-54-6020, dated February 22, 1994: Prior to the accumulation of 
5,700 total landings, or within 500 landings after the effective 
date of this AD, whichever occurs later, perform an internal eddy 
current inspection to detect cracks in the lower spar axis of the 
pylons between ribs 6 and 7, in accordance with Airbus Industrie 
Service Bulletin A300-54-6014, Revision 1, dated March 28, 1994.
    (1) If no crack is found, repeat the inspection thereafter at 
intervals not to exceed 4,400 landings.
    (2) If any crack is found that is less than 35 mm, prior to 
further flight, stop-drill the crack in accordance with the 
procedures specified in Section 51-41-10 of the SRM. Thereafter, 
prior to the accumulation of 250 landings after crack discovery, 
repair in accordance with the service bulletin. Prior to the 
accumulation of 10,100 landings after accomplishing the repair, 
perform an eddy current inspection to detect cracks at the stiffener 
ends, ribs 6 and 7, at the edge of the holes made during the repair 
and on the fasteners located at the edge of the doubler, in 
accordance with the service bulletin.
    (i) If no crack is found, repeat the inspection required by 
paragraph (g)(2) of this AD thereafter at intervals not to exceed 
10,000 landings.
    (ii) If any crack is found, prior to further flight, repair in 
accordance with a method approved by the Manager, Standardization 
Branch, ANM-113.
    (3) If any crack is found that is greater than or equal to 35 
mm, prior to further flight, repair in accordance with a method 
approved by the Manager, Standardization Branch, ANM-113.
    (h) For Model A300-600 series airplanes equipped with Pratt & 
Whitney JT9D-7R4 or PW 4000 engines, and having pylons that have 
been modified in accordance with Airbus Industrie Service Bulletin 
A300-54-6020, dated February 22, 1994: Prior to the accumulation of 
17,000 landings since installation of the modification, or within 
500 landings after the effective date of this AD, whichever occurs 
later, perform an eddy current inspection to detect cracks in the 
lower spar axis of the pylons between ribs 6 and 7, in accordance 
with Airbus Industrie Service Bulletin A300-54-6014, Revision 1, 
dated March 28, 1994.

[[Page 26094]]

    (1) If no crack is found, repeat the eddy current inspection 
thereafter at intervals not to exceed 14,500 landings.
    (2) If any crack is found, prior to further flight, repair in 
accordance with a method approved by the Manager, Standardization 
Branch, ANM-113.
    (i) For Model A310 series airplanes equipped with General 
Electric CF6-80C2, or Pratt & Whitney JT9D-7R4, or Pratt & Whitney 
PW4000 engines: Prior to the accumulation of 36,700 total landings, 
or within 500 landings after the effective date of this AD, 
whichever occurs later, perform an internal eddy current inspection 
to detect cracks in the lower spar axis of the pylons between ribs 6 
and 7, in accordance with Airbus Industrie Service Bulletin A310-54-
2017, Revision 1, dated March 28, 1994.
    (1) If no crack is found, repeat the inspection thereafter at 
intervals not to exceed 15,000 landings.
    (2) If any crack is found that is less than 35 mm, prior to 
further flight, stop-drill the crack in accordance with the 
procedures specified in Section 51-41-10 of the SRM. Thereafter, 
prior to the accumulation of 250 landings after crack discovery, 
repair in accordance with the service bulletin. Prior to the 
accumulation of 40,000 landings after accomplishing the repair, 
perform an eddy current inspection to detect cracks at the stiffener 
ends, ribs 6 and 7, at the edge of the holes made during the repair 
and on the fasteners located at the edge of the doubler, in 
accordance with the service bulletin.
    (i) If no crack is found, repeat the inspection required by 
paragraph (i)(2) of this AD thereafter at intervals not to exceed 
33,000 landings.
    (ii) If any crack is found, prior to further flight, repair in 
accordance with a method approved by the Manager, Standardization 
Branch, ANM-113.
    (3) If any crack is found that is greater than or equal to 35 
mm, prior to further flight, repair in accordance with a method 
approved by the Manager, Standardization Branch, ANM-113.
    (j) For Model A310 series airplanes equipped with General 
Electric CF6-80C2, or Pratt & Whitney JT9D-7R4, or Pratt & Whitney 
PW4000 engines: Accomplishment of the modification specified in 
Airbus Industrie Service Bulletin A310-54-2023, dated October 15, 
1993, constitutes terminating action for the inspections required by 
paragraph (i) of this AD.
    (k) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Standardization Branch, ANM-113. 
Operators shall submit their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Standardization Branch, ANM-113.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Standardization Branch, ANM-113.

    (l) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.
    (m) The actions shall be done in accordance with the following 
Airbus Industrie service bulletins, which contain the specified 
effective pages:

----------------------------------------------------------------------------------------------------------------
Service bulletin referenced and                                 Revision level shown on                         
              date                         Page No.-                      page              Date shown on page  
----------------------------------------------------------------------------------------------------------------
A300-54-0073, Revision 1, March  1,5..........................  1......................  Mar. 28, 1994.         
 28, 1994.                                                                                                      
                                 2-4, 6-36....................  Original...............  Oct. 15, 1993.         
A300-54-6014, Revision 1, March  1-4, 13......................  1......................  Mar. 28, 1994.         
 28, 1994.                                                                                                      
                                 5-12, 14-44..................  Original...............  Oct. 15, 1993.         
A310-54-2017, Revision 1, March  1, 5,........................  1......................  Mar. 28, 1994.         
 28, 1994.                                                                                                      
                                 2-4, 6-48....................  Original...............  Oct. 15, 1993.         
A310-54-2023, October 15, 1993.  1-38.........................  Original...............  Oct. 15, 1993.         
----------------------------------------------------------------------------------------------------------------

This incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from Airbus Industrie, 1 Rond Point 
Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be 
inspected at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
    (n) This amendment becomes effective on June 28, 1996.

    Issued in Renton, Washington, on May 15, 1996.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-12731 Filed 5-23-96; 8:45 am]
BILLING CODE 4910-13-U